固体火箭技术2025，Vol.48Issue(5)：791-798,8.DOI:10.7673/j.issn.1006-2793.2025.05.018
冷气微霍尔推力器推力响应时间测量方法研究
Measurement of response time of micro-Hall thruster in cold air mode
摘要
Abstract
The rapid response measurement of micro-thruster thrust is of great significance to the drag-free control system.In or-der to meet the demand of the drag-free control system for rapid response of thrust measurement,a new method of thruster beam pa-rameter diagnosis of thrust response was proposed.Based on the four-stage self-stabilized ionization gauge probe,a cold gas micro-thruster thrust rapid measurement system was built,and the physical model of thrust response time was established.Combined with the high-precision acquisition control circuit,the thrust response time was converted into the probe collector current change time,so as to obtain the thrust response time.In the experiment,the cold electric dual-mode micro-Hall thruster was used as the test object.The control variable method was used to change a single experimental condition,and the response time was measured multiple times to obtain the influence of the appropriate anode flow range,accelerating electrode voltage and axial distance on the response time measurement.The experimental results show that the response time of the measurement system based on the four-stage self-stabilized ionization gauge probe is less than 35 ms,and the thrust response index of 50 ms can be achieved.关键词
微推力器/冷气模式/推力测试/响应时间/实验测试Key words
micro-thruster/cold gas mode/thrust test/response time/experimental test分类
航空航天引用本文复制引用
龙涛,龙建飞,王嘉彬,周炜杰,郭大伟,孙明明,赵呈选,郭宁..冷气微霍尔推力器推力响应时间测量方法研究[J].固体火箭技术,2025,48(5):791-798,8.基金项目
国家重点研发计划(2021YFC2202700) （2021YFC2202700）
国科大杭州高等研究院专项资金资助项目(2022ZZ01009). （2022ZZ01009）
